Flexible coupling for geared turbine engine
First Claim
Patent Images
1. A gas turbine engine comprising:
- a fan shaft arranged along an engine central axis;
a frame supporting the fan shaft;
a gear system rotatably coupled with the fan shaft; and
a flexible coupling at least partially supporting the gear system, the flexible coupling defining, with respect to the engine central axis, a torsional stiffness TS and a lateral stiffness LS such that a ratio of TS/LS is greater than or equal to about 2.0 to reduce loads on the gear system from misalignment of the gear system with respect to the engine central axis.
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Abstract
A gas turbine engine includes a fan shaft arranged along an engine central axis, a frame supporting the fan shaft, a gear system rotatably coupled with the fan shaft, and a flexible coupling at least partially supporting the gear system. The flexible coupling defines, with respect to the engine central axis, a torsional stiffness TS and a lateral stiffness LS such that a ratio of TS/LS is greater than or equal to about 2.0 to reduce loads on the gear system from misalignment of the gear system with respect to the engine central axis.
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Citations
19 Claims
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1. A gas turbine engine comprising:
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a fan shaft arranged along an engine central axis; a frame supporting the fan shaft; a gear system rotatably coupled with the fan shaft; and a flexible coupling at least partially supporting the gear system, the flexible coupling defining, with respect to the engine central axis, a torsional stiffness TS and a lateral stiffness LS such that a ratio of TS/LS is greater than or equal to about 2.0 to reduce loads on the gear system from misalignment of the gear system with respect to the engine central axis. - View Dependent Claims (2, 3, 4)
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5. A gas turbine engine comprising:
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a fan shaft arranged along an engine central axis; a frame supporting the fan shaft, the frame defining a frame lateral stiffness FLS; a gear system rotatably coupled to the fan shaft; a first flexible coupling and a second flexible coupling at least partially supporting the gear system, the first flexible coupling and the second flexible coupling being subject to at least one type of motion, with respect to the engine central axis, selected from the group consisting of Motion I, Motion II, Motion III, Motion IV and combinations thereof, wherein Motion I is parallel offset guided end motion, Motion II is cantilever beam free end motion and Motion III is angular misalignment no offset motion and Motion IV is axial motion, the first flexible coupling having a first stiffness defined with respect to the frame lateral stiffness FLS and the type of motion and the second flexible coupling having a second stiffness defined with respect the frame lateral stiffness FLS and the type of motion. - View Dependent Claims (6, 7, 8, 9, 10, 11)
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12. A gas turbine engine comprising:
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a fan shaft arranged along an engine central axis; a frame supporting the fan shaft, the frame defining a frame lateral stiffness FLS; a gear system rotatably coupled to the fan shaft; and a first flexible coupling and a second flexible coupling at least partially supporting the gear system, the first flexible coupling and the second flexible coupling being subject to at least one type of motion, with respect to the engine central axis, selected from the group consisting of Motion I, Motion II, Motion III, Motion IV and combinations thereof, wherein, Motion I is parallel offset guided end motion, Motion II is cantilever beam free end motion and Motion III is angular misalignment no offset motion and Motion IV is axial motion, the first flexible coupling and the second flexible each having Stiffnesses A, B, C, D and E defined with respect to the frame lateral stiffness FLS, wherein Stiffness A is axial stiffness under Motion IV, Stiffness B is radial stiffness under Motion II, Stiffness C is radial stiffness under Motion I, Stiffness D is torsional stiffness under Motion I, and Stiffness E is angular stiffness under Motion III. - View Dependent Claims (13, 14, 15, 16, 17, 18, 19)
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Specification